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ドライアイス推進剤供給システムの真空環境下における運用実証
https://jaxa.repo.nii.ac.jp/records/49511
https://jaxa.repo.nii.ac.jp/records/49511eb47d52d-5b69-4eb5-accb-09c67722c8d4
名前 / ファイル | ライセンス | アクション |
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SA6000184055.pdf (810.7 kB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2023-05-23 | |||||
タイトル | ||||||
タイトル | ドライアイス推進剤供給システムの真空環境下における運用実証 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Operational demonstration of propellant supply system using dry ice as propellant in a vacuum environment | |||||
著者 |
野坂, 俊介
× 野坂, 俊介× 杵淵, 紀世志× 張, 科寅× 渡邊, 裕樹× NOSAKA, Shunsuke× KINEFUCHI, Kiyoshi× CHO, Shinatora× WATANABE, Hiroki |
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著者所属 | ||||||
名古屋大学大学院 | ||||||
著者所属 | ||||||
名古屋大学 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Nagoya University | ||||||
著者所属(英) | ||||||
en | ||||||
Nagoya University | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS) | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS) | |||||
書誌情報 |
令和4年度宇宙輸送シンポジウム: 講演集録 en : Proceedings of Space Transportation Symposium FY2022 発行日 2023-01 |
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会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 令和4年度宇宙輸送シンポジウム(2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)) , 相模原市, 神奈川県 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Dry ice is proposed as an alternative to xenon, which is currently widely used as a propellant for electric propulsion, due to its overwhelmingly lower price. Furthermore, by storing CO2 in a triple point, it can be stored at low pressure and supplied to the propellant at a constant flow rate. A mathematical model has been developed to determine the phase characteristics in the tank, which are determined by the heat input to the tank and the propellant flow rate. In the mathematical model, the liquid phase decreases with propellant supply during on-orbit operation, and the triple point is finished. Therefore, an experiment was conducted in which the tank was placed in a vacuum and the propellant was discharged to compare with the mathematical model. In the experiment, when the propellant was discharged more than 147 sccm at 2W heat input, the pressure dropped along the vapor-liquid equilibrium line. In the mathematical model, the liquid phase decreases when discharging more than 110 sccm at 2W heat input, and this comparison shows that there is a difference of about 28% from the experimental value. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 所属の誤記: The University of Nagoya | |||||
著者版フラグ | ||||||
出版タイプ | AM | |||||
出版タイプResource | http://purl.org/coar/version/c_ab4af688f83e57aa | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA6000184055 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | STEP-2022-003 |